Serial/Series Title
451 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
451
next
A Flight-Test Study of Total-Pressure Distortion in a Thick-Lipped Nose Inlet
Memorandum presenting flight tests conducted on a thick-lipped nose inlet of a transonic swept-wing aircraft. The total-pressure recovery and distortion at the compressor face were measured over the maneuvering range of the airplane for Mach numbers up to 1.03. Results regarding the radial total-pressure profile, average total-pressure recovery, and total-pressure distortion are provided.
Date:
June 30, 1958
Creator:
Wingrove, Rodney C.
System:
The UNT Digital Library
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date:
June 30, 1958
Creator:
Turner, Kenneth L. & Appich, W. H., Jr.
System:
The UNT Digital Library
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Report presenting an investigation in the Unitary Plan wind tunnel to determine the static stability characteristics of five hypersonic missile configurations. Tests were performed at a range of Mach and Reynolds numbers based on body length. Results regarding the effect of a base block, longitudinal and directional stability, and Reynolds number effect are provided.
Date:
June 30, 1958
Creator:
Turner, Kenneth L. & Appich, W. H., Jr.
System:
The UNT Digital Library
Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20
Report presenting an investigation to determine the experimental and predicted wave-drag characteristics of wing-body combinations. Two yawed wings, each with an average sweep of about 40 degrees, were tested with various bodies, and the results were compared with existing data for similar models with sweptback wings. Results regarding the aerodynamic characteristics and pressure results are provided.
Date:
June 30, 1958
Creator:
Holdaway, George H. & Hatfield, Elaine W.
System:
The UNT Digital Library
Viscous Flows in Inlets
Report discusses ways to reduce "viscous effects", which increase total pressure losses due to friction at increasing free-stream Mach numbers. Some of the effects are related to the inlet of an aircraft and potential issues in design. From Introduction: "Care must be exercised in inlet design to maintain uniform steady boundary-layer and core flows in the throat."
Date:
June 30, 1958
Creator:
Scherrer, Richard; Lundell, John H. & Anderson, Lewis A.
System:
The UNT Digital Library
Experimental investigation of the drag due to wedges along the trailing edge of a swept wing
Report presenting a wind-tunnel investigation to determine the drag increment due to the superposition of the wedges with various plan-form shapes along the trailing edge of a sweptback wing.
Date:
June 27, 1958
Creator:
Gambucci, Bruno J. & Wyss, John A.
System:
The UNT Digital Library
Hydrodynamic Characteristics of Missiles Launched Under Water
Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date:
June 27, 1958
Creator:
Dawson, John R.
System:
The UNT Digital Library
Maneuver Performance of Interceptor Missiles
"From these preliminary wind-tunnel tests of interceptor missile configurations and the analysis of point defense against ballistic missiles, it is concluded that adequate aerodynamic lift is readily available and should be utilized when operating under high-dynamic-pressure conditions and that more work should be done on controls, either aerodynamic or reaction type, so that the configurations may be trimmed to the angles of attack required to develop the necessary turning force" (p. 5).
Date:
June 27, 1958
Creator:
Stone, David G.
System:
The UNT Digital Library
The Prospects for Laminar Flow on Hypersonic Airplanes
The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.
Date:
June 27, 1958
Creator:
Seiff, Alvin
System:
The UNT Digital Library
Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System
Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date:
June 25, 1958
Creator:
Smith, Arthur L. & Grobman, Jack S.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 45 Degree Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
System:
The UNT Digital Library
Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.
Date:
June 24, 1958
Creator:
Lord, Douglas R.
System:
The UNT Digital Library
Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data
"A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results" (p. 1).
Date:
June 24, 1958
Creator:
Shanks, Robert E.
System:
The UNT Digital Library
An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers From 3.0 to 6.3
Memorandum presenting static longitudinal stability and control characteristics of a flare-stabilized body of revolution employing a movable portion of the flare surface as a pitch control determined for a range of Mach numbers, angles of attack, and control deflections. The variation of lift coefficient with pitching-moment coefficient for the basic configuration with control undeflected was found to be essentially linear, and the stability to increase slightly with increasing Mach number.
Date:
June 24, 1958
Creator:
Gloria, Hermilo R.
System:
The UNT Digital Library
Some Effects of Mass Ratio on the Transonic Flutter Characteristics of Untapered 45 Degree Sweptback Wings of Aspect Ratios 2 and 3.5
Report presenting a study of the effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5. A given wing at a given Mach number fluttered at essentially a fixed dynamic pressure regardless of the individual values of the fluid velocity and density. Results regarding the experimental data, analytical results, and a comparison of the two, are provided.
Date:
June 24, 1958
Creator:
Kelly, H. Neale
System:
The UNT Digital Library
Data From Flow-Field Surveys Behind a Large-Scale Thin Straight Wing of Aspect Ratio 3
Memorandum presenting limited flow-field surveys made behind a large-scale thin straight wing of aspect ratio 3, both alone and in combination with a body and vertical tail. The surveys indicated a region of high downwash angles, low dynamic pressures, and rough flow, that extended higher above the wing chord plane, and farther aft, with increasing angle of attack beyond the tail.
Date:
June 23, 1958
Creator:
Evans, William T.
System:
The UNT Digital Library
Effect of aerodynamic heating on the flutter of a rectangular wing at a Mach number of 2
Report presenting the flutter of a solid wing as affected by aerodynamic heating, which can cause a large momentary loss in torsional stiffness. Both experimental and analytical studies were conducted and good correlation was demonstrated. The loss of stiffness due to aerodynamic heating was calculated and the operational line intersected with the flutter curve.
Date:
June 23, 1958
Creator:
Runyan, Harry L. & Jones, Nan H.
System:
The UNT Digital Library
Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51
Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date:
June 23, 1958
Creator:
Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
System:
The UNT Digital Library
Some Factors Affecting the Stability and Performance Characteristics of Canard Aircraft Configurations
"A survey has been made of some of the factors to be considered in the design of canard aircraft configurations. The factors include Mach number and angle-of-attack effects as well as the effects of various geometric changes. Among the geometric variables included are the effects of wing plan form, wing height, wing twist, canard plan form, canard area, canard moment arm, forebody length, afterbody length, forebody deflection, vertical-tail plan form, vertical-tail size, vertical-tail location, and various ventral-fin arrangements" (p. 1).
Date:
June 23, 1958
Creator:
Spearman, M. Leroy & Driver, Cornelius
System:
The UNT Digital Library
Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: An Aluminum-Alloy Model of 40-Inch Chord With 0.125-Inch-Thick Skin
Report presenting testing of a 5-percent-thick 2024-T3 aluminum-alloy multiweb wing (MW-1-(2)) at a Mach number of 2 under simulated supersonic flight conditions. The wing experienced dynamic failure as a result of catastrophic flag-waving flutter due to the combined action of aerodynamic heating and loading. Results regarding model temperatures, experimental pressures, strain results, accelerometer, and model failure are provided.
Date:
June 23, 1958
Creator:
Griffith, George E. & Miltonberger, Georgene H.
System:
The UNT Digital Library
Analytical and experimental investigation of a temperature-schedule acceleration control for a turbojet engine
From Introduction: "This report investigates some of the problems involved in scheduling the tailpipe temperature to avoid stall during acceleration. The object of this report is to investigate the dynamics of a closed-loop acceleration control that follows a schedule of tailpipe temperature with rotor speed."
Date:
June 22, 1958
Creator:
Heppler, Herbert; Stiglic, Paul M. & Novik, David
System:
The UNT Digital Library
Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58
Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date:
June 20, 1958
Creator:
Hollinger, James A.
System:
The UNT Digital Library
Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58: Coord. No. AF-204
Memorandum presenting a longitudinal stability and control investigation made over a range of Mach numbers of a scale model of the Convair B-58 external store. Normal force, chord force, and static and dynamic stability derivatives formed an important part of the results. Results regarding the hinge moments and longitudinal trim and force coefficients are also provided.
Date:
June 20, 1958
Creator:
Hollinger, James A.
System:
The UNT Digital Library